The technical objectives of the research are to establish the minimum level of modeling necessary for predicting the dynamic stresses in fighter aircraft during maneuvers and transitions between maneuvers, to identity the physical phenomena which are significant, to identity potential short falls in current aircraft design technology and to identity areas for further research. A symmetric wing, modeled as a beam with quasi-steady aerodynamic loads introduced through the vortex lattice method, is used for the dynamic evaluation. The dynamically equations of motion are solved in the time domain by the Runge-Kutta method specialized to second order equations. The maneuver dynamic analysis program, MANDYN, written in Fortran 77, uses the parameters of real variable-geometry airplane. An extensive investigation of dynamic loads resulting from a simple maneuver for various severity levels revealed that the lowest natural frequency and load application time are significant factors in determining the validity of the load factor approach. Recommendations based on the study results are made.
Structural dynamics of maneuvering aircraft
Strukturdynamik von manoevrierenden Flugzeugen
US Government Reports ; Sep ; 1-90
1987
90 Seiten
Report
English
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